Abstract
This study deals with orbital transfer of a tethered satellite system (TSS) on orbit. Dynamics of TSS is restricted to the angular momentum conservation law of the system around a planet. This constraint is not integrable (, that is called "nonholonomic constraint"), and the final state of TSS depends on a time history of the input. While previous works for orbital transfer mainly investigated dynamics of the system for specified time profiles of the tether-length, this study aims to make tether extension profiles to achieve some specified orbit. This paper, as a preliminary study, gives a brief overview of the previous works and investigates the fundamental property of the constraint based on the angular momentum conservation. Integrability and accessibility /controllability are analyzed and also numerically verified. For simplicity, TSS is modeled to a dumbbell-type satellite in this study.
| Original language | English |
|---|---|
| Title of host publication | International Astronautical Federation - 55th International Astronautical Congress 2004 |
| Pages | 751-756 |
| Number of pages | 6 |
| Volume | 2 |
| Publication status | Published - 2004 |
| Event | International Astronautical Federation - 55th International Astronautical Congress 2004 - Vancouver, Canada Duration: Oct 4 2004 → Oct 8 2004 |
Other
| Other | International Astronautical Federation - 55th International Astronautical Congress 2004 |
|---|---|
| Country | Canada |
| City | Vancouver |
| Period | 10/4/04 → 10/8/04 |
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All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Space and Planetary Science
Cite this
Considerations on control for a tethered satellite system through angular momentum conservation. / Hokamoto, Shinji.
International Astronautical Federation - 55th International Astronautical Congress 2004. Vol. 2 2004. p. 751-756.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Considerations on control for a tethered satellite system through angular momentum conservation
AU - Hokamoto, Shinji
PY - 2004
Y1 - 2004
N2 - This study deals with orbital transfer of a tethered satellite system (TSS) on orbit. Dynamics of TSS is restricted to the angular momentum conservation law of the system around a planet. This constraint is not integrable (, that is called "nonholonomic constraint"), and the final state of TSS depends on a time history of the input. While previous works for orbital transfer mainly investigated dynamics of the system for specified time profiles of the tether-length, this study aims to make tether extension profiles to achieve some specified orbit. This paper, as a preliminary study, gives a brief overview of the previous works and investigates the fundamental property of the constraint based on the angular momentum conservation. Integrability and accessibility /controllability are analyzed and also numerically verified. For simplicity, TSS is modeled to a dumbbell-type satellite in this study.
AB - This study deals with orbital transfer of a tethered satellite system (TSS) on orbit. Dynamics of TSS is restricted to the angular momentum conservation law of the system around a planet. This constraint is not integrable (, that is called "nonholonomic constraint"), and the final state of TSS depends on a time history of the input. While previous works for orbital transfer mainly investigated dynamics of the system for specified time profiles of the tether-length, this study aims to make tether extension profiles to achieve some specified orbit. This paper, as a preliminary study, gives a brief overview of the previous works and investigates the fundamental property of the constraint based on the angular momentum conservation. Integrability and accessibility /controllability are analyzed and also numerically verified. For simplicity, TSS is modeled to a dumbbell-type satellite in this study.
UR - http://www.scopus.com/inward/record.url?scp=34249051971&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=34249051971&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:34249051971
VL - 2
SP - 751
EP - 756
BT - International Astronautical Federation - 55th International Astronautical Congress 2004
ER -